Airfoil: E231 Builder: M. Lachowski Comment: clean Number of Reynolds #'s: 7 Average Reynolds #: 60900 Number of angles of attack: 15 alpha / Cl / Cd / Spanwise Cd's >>> -2.51 -0.223 0.0197 0.0233 0.0180 0.0192 0.0183 -1.44 -0.124 0.0204 0.0192 0.0190 0.0226 0.0207 -0.44 -0.021 0.0230 0.0236 0.0229 0.0238 0.0215 0.59 0.071 0.0275 0.0277 0.0295 0.0258 0.0267 1.61 0.141 0.0310 0.0398 0.0276 0.0268 0.0299 2.62 0.214 0.0391 0.0400 0.0372 0.0408 0.0383 3.67 0.282 0.0437 0.0475 0.0421 0.0416 0.0436 4.67 0.365 0.0499 0.0489 0.0494 0.0508 0.0505 5.75 0.504 0.0515 0.0536 0.0508 0.0508 0.0509 6.75 0.734 0.0362 0.0409 0.0278 0.0372 0.0391 7.81 0.840 0.0318 0.0382 0.0246 0.0314 0.0330 8.79 0.901 0.0333 0.0374 0.0240 0.0402 0.0315 9.82 0.953 0.0394 0.0385 0.0359 0.0405 0.0427 10.81 0.992 0.0442 0.0455 0.0488 0.0391 0.0434 11.86 1.027 0.0539 0.0516 0.0589 0.0537 0.0515 Tabulated from data in file CL01252.DAT & reduced using program Q05.01D Average Reynolds #: 60800 Number of angles of attack: 2 alpha / Cl / Cd / Spanwise Cd's >>> -4.57 -0.452 0.0276 0.0268 0.0283 0.0255 0.0298 -3.53 -0.363 0.0219 0.0189 0.0241 0.0201 0.0244 Tabulated from data in file CL01256.DAT & reduced using program Q05.01D Average Reynolds #: 99900 Number of angles of attack: 14 alpha / Cl / Cd / Spanwise Cd's >>> -2.50 -0.210 0.0188 0.0197 0.0190 0.0182 0.0183 -1.44 -0.024 0.0219 0.0222 0.0204 0.0225 0.0225 -0.36 0.067 0.0225 0.0228 0.0218 0.0230 0.0225 0.65 0.120 0.0253 0.0264 0.0247 0.0254 0.0248 1.66 0.185 0.0293 0.0298 0.0297 0.0296 0.0281 2.62 0.260 0.0331 0.0341 0.0342 0.0325 0.0318 3.70 0.380 0.0367 0.0375 0.0377 0.0365 0.0350 4.77 0.608 0.0302 0.0309 0.0300 0.0299 0.0300 5.73 0.734 0.0231 0.0236 0.0232 0.0234 0.0223 6.78 0.839 0.0189 0.0186 0.0189 0.0191 0.0189 7.82 0.929 0.0198 0.0210 0.0203 0.0190 0.0189 8.82 0.994 0.0242 0.0232 0.0221 0.0242 0.0273 9.87 1.040 0.0303 0.0302 0.0296 0.0322 0.0293 10.83 1.080 0.0359 0.0346 0.0336 0.0379 0.0377 Tabulated from data in file CL01254.DAT & reduced using program Q05.01D Average Reynolds #: 101900 Number of angles of attack: 2 alpha / Cl / Cd / Spanwise Cd's >>> -4.54 -0.371 0.0264 0.0278 0.0259 0.0253 0.0264 -3.53 -0.283 0.0219 0.0211 0.0212 0.0226 0.0228 Tabulated from data in file CL01255.DAT & reduced using program Q05.01D Average Reynolds #: 200600 Number of angles of attack: 16 alpha / Cl / Cd / Spanwise Cd's >>> -4.56 -0.238 0.0195 0.0204 0.0190 0.0195 0.0192 -3.48 -0.159 0.0175 0.0179 0.0168 0.0172 0.0181 -2.35 -0.095 0.0148 0.0149 0.0146 0.0144 0.0150 -1.38 -0.021 0.0163 0.0148 0.0169 0.0163 0.0170 -0.29 0.153 0.0185 0.0206 0.0181 0.0161 0.0191 0.61 0.306 0.0149 0.0166 0.0167 0.0132 0.0130 1.78 0.425 0.0160 0.0159 0.0163 0.0163 0.0156 2.73 0.506 0.0155 0.0151 0.0159 0.0156 0.0153 3.69 0.590 0.0147 0.0141 0.0151 0.0148 0.0148 4.72 0.703 0.0131 0.0126 0.0136 0.0130 0.0131 5.75 0.795 0.0124 0.0123 0.0123 0.0122 0.0129 6.82 0.882 0.0135 0.0130 0.0135 0.0135 0.0137 7.84 0.943 0.0163 0.0159 0.0160 0.0164 0.0168 8.85 0.999 0.0204 0.0197 0.0199 0.0212 0.0209 9.83 1.052 0.0244 0.0231 0.0245 0.0246 0.0254 10.84 1.099 0.0294 0.0279 0.0287 0.0302 0.0308 Tabulated from data in file CL01258.DAT & reduced using program Q05.01D Average Reynolds #: 301000 Number of angles of attack: 16 alpha / Cl / Cd / Spanwise Cd's >>> -4.57 -0.284 0.0168 0.0173 0.0171 0.0163 0.0165 -3.39 -0.177 0.0150 0.0150 0.0154 0.0146 0.0150 -2.26 -0.090 0.0120 0.0123 0.0120 0.0121 0.0117 -1.51 -0.039 0.0113 0.0112 0.0115 0.0111 0.0113 -0.44 0.050 0.0123 0.0135 0.0111 0.0118 0.0127 0.57 0.160 0.0112 0.0108 0.0121 0.0109 0.0110 1.72 0.382 0.0117 0.0103 0.0139 0.0120 0.0106 2.78 0.518 0.0108 0.0083 0.0124 0.0120 0.0105 3.75 0.627 0.0102 0.0094 0.0108 0.0104 0.0103 4.72 0.723 0.0100 0.0096 0.0106 0.0098 0.0100 5.74 0.820 0.0106 0.0103 0.0109 0.0104 0.0107 6.83 0.902 0.0126 0.0120 0.0125 0.0126 0.0131 7.85 0.954 0.0151 0.0146 0.0148 0.0150 0.0159 8.86 1.019 0.0180 0.0174 0.0178 0.0179 0.0190 9.83 1.080 0.0216 0.0204 0.0214 0.0223 0.0225 10.85 1.130 0.0262 0.0223 0.0266 0.0306 0.0253 Tabulated from data in file CL01260.DAT & reduced using program Q05.01D Average Reynolds #: 400400 Number of angles of attack: 16 alpha / Cl / Cd / Spanwise Cd's >>> -4.53 -0.302 0.0146 0.0149 0.0149 0.0141 0.0146 -3.48 -0.203 0.0133 0.0133 0.0138 0.0128 0.0132 -2.47 -0.110 0.0113 0.0114 0.0114 0.0113 0.0111 -1.44 -0.034 0.0089 0.0089 0.0090 0.0090 0.0086 -0.34 0.064 0.0094 0.0100 0.0094 0.0090 0.0091 0.64 0.182 0.0097 0.0106 0.0101 0.0095 0.0084 1.69 0.314 0.0088 0.0082 0.0116 0.0083 0.0073 2.66 0.439 0.0084 0.0074 0.0107 0.0079 0.0076 3.75 0.589 0.0093 0.0085 0.0112 0.0077 0.0098 4.78 0.724 0.0085 0.0061 0.0117 0.0071 0.0093 5.83 0.835 0.0094 0.0093 0.0117 0.0082 0.0084 6.80 0.905 0.0120 0.0117 0.0124 0.0121 0.0120 7.80 0.945 0.0143 0.0136 0.0139 0.0147 0.0150 8.83 1.013 0.0169 0.0160 0.0164 0.0176 0.0176 9.86 1.085 0.0200 0.0182 0.0196 0.0219 0.0203 10.86 1.128 0.0243 0.0198 0.0236 0.0301 0.0237 Tabulated from data in file CL01262.DAT & reduced using program Q05.01D File E231.DRG created on 09-12-1997 at 13:39:49 using program FORMAT